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NACA-RM-L52K06
Pressure distribution and pressure drag for a hemispherical nose at Mach numbers 2.05, 2.54, and 3.04
Year: 1952
Abstract: INTRODUCTION
From the standpoint of minimum drag, high fineness ratios and nearly pointed noses are desirable in the design of supersonic missiles and airplanes. However, it is necessary for some supersonic vehicles to have a hemispherical nose to house guidance equipment. Since use of this nose shape may result in severe drag penalties, with corresponding reduction in speed and range, the National Advisory Committee for Aeronautics has made tests in the preflight jet and in free flight to determine the pressure drag, pressure distribution, and aerodynamic heating of hemispherical nose bodies. The tests were made at Langley Pilotless Aircraft Research Station at Wallops Island, Va. Flight tests to determine the drag of several round-nosed bodies at supersonic speeds have been reported in reference 1. The present paper presents the data obtained from pressure measurements at Mach numbers of 2.05, 2.54, and 3.04 and for Reynolds numbers of 4.44 x 106, 4.57 x 106, and 4.16 x 106, respectively. The Reynolds number was based on body diameter and free-stream condition.
From the standpoint of minimum drag, high fineness ratios and nearly pointed noses are desirable in the design of supersonic missiles and airplanes. However, it is necessary for some supersonic vehicles to have a hemispherical nose to house guidance equipment. Since use of this nose shape may result in severe drag penalties, with corresponding reduction in speed and range, the National Advisory Committee for Aeronautics has made tests in the preflight jet and in free flight to determine the pressure drag, pressure distribution, and aerodynamic heating of hemispherical nose bodies. The tests were made at Langley Pilotless Aircraft Research Station at Wallops Island, Va. Flight tests to determine the drag of several round-nosed bodies at supersonic speeds have been reported in reference 1. The present paper presents the data obtained from pressure measurements at Mach numbers of 2.05, 2.54, and 3.04 and for Reynolds numbers of 4.44 x 106, 4.57 x 106, and 4.16 x 106, respectively. The Reynolds number was based on body diameter and free-stream condition.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:09:22Z | |
| date available | 2017-09-04T17:09:22Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | YMSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/132860 | |
| description abstract | INTRODUCTION From the standpoint of minimum drag, high fineness ratios and nearly pointed noses are desirable in the design of supersonic missiles and airplanes. However, it is necessary for some supersonic vehicles to have a hemispherical nose to house guidance equipment. Since use of this nose shape may result in severe drag penalties, with corresponding reduction in speed and range, the National Advisory Committee for Aeronautics has made tests in the preflight jet and in free flight to determine the pressure drag, pressure distribution, and aerodynamic heating of hemispherical nose bodies. The tests were made at Langley Pilotless Aircraft Research Station at Wallops Island, Va. Flight tests to determine the drag of several round-nosed bodies at supersonic speeds have been reported in reference 1. The present paper presents the data obtained from pressure measurements at Mach numbers of 2.05, 2.54, and 3.04 and for Reynolds numbers of 4.44 x 106, 4.57 x 106, and 4.16 x 106, respectively. The Reynolds number was based on body diameter and free-stream condition. | |
| language | English | |
| title | NACA-RM-L52K06 | num |
| title | Pressure distribution and pressure drag for a hemispherical nose at Mach numbers 2.05, 2.54, and 3.04 | en |
| type | standard | |
| page | 15 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |